EP3658462A1 - Installation d'usinage pour éléments structuraux d'avions - Google Patents

Installation d'usinage pour éléments structuraux d'avions

Info

Publication number
EP3658462A1
EP3658462A1 EP18722010.8A EP18722010A EP3658462A1 EP 3658462 A1 EP3658462 A1 EP 3658462A1 EP 18722010 A EP18722010 A EP 18722010A EP 3658462 A1 EP3658462 A1 EP 3658462A1
Authority
EP
European Patent Office
Prior art keywords
upper tool
tool
unit
tool unit
axis
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP18722010.8A
Other languages
German (de)
English (en)
Other versions
EP3658462B1 (fr
Inventor
Nils Varrelmann
Volker Neemann
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Broetje Automation GmbH
Original Assignee
Broetje Automation GmbH
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Broetje Automation GmbH filed Critical Broetje Automation GmbH
Publication of EP3658462A1 publication Critical patent/EP3658462A1/fr
Application granted granted Critical
Publication of EP3658462B1 publication Critical patent/EP3658462B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
    • B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
    • B64F5/10—Manufacturing or assembling aircraft, e.g. jigs therefor
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
    • B21J—FORGING; HAMMERING; PRESSING METAL; RIVETING; FORGE FURNACES
    • B21J13/00—Details of machines for forging, pressing, or hammering
    • B21J13/08—Accessories for handling work or tools
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
    • B21J—FORGING; HAMMERING; PRESSING METAL; RIVETING; FORGE FURNACES
    • B21J15/00—Riveting
    • B21J15/10—Riveting machines
    • B21J15/14—Riveting machines specially adapted for riveting specific articles, e.g. brake lining machines
    • B21J15/142—Aerospace structures
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
    • B21J—FORGING; HAMMERING; PRESSING METAL; RIVETING; FORGE FURNACES
    • B21J15/00—Riveting
    • B21J15/38—Accessories for use in connection with riveting, e.g. pliers for upsetting; Hand tools for riveting
    • B21J15/42—Special clamping devices for workpieces to be riveted together, e.g. operating through the rivet holes
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23Q—DETAILS, COMPONENTS, OR ACCESSORIES FOR MACHINE TOOLS, e.g. ARRANGEMENTS FOR COPYING OR CONTROLLING; MACHINE TOOLS IN GENERAL CHARACTERISED BY THE CONSTRUCTION OF PARTICULAR DETAILS OR COMPONENTS; COMBINATIONS OR ASSOCIATIONS OF METAL-WORKING MACHINES, NOT DIRECTED TO A PARTICULAR RESULT
    • B23Q1/00—Members which are comprised in the general build-up of a form of machine, particularly relatively large fixed members
    • B23Q1/25—Movable or adjustable work or tool supports
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23Q—DETAILS, COMPONENTS, OR ACCESSORIES FOR MACHINE TOOLS, e.g. ARRANGEMENTS FOR COPYING OR CONTROLLING; MACHINE TOOLS IN GENERAL CHARACTERISED BY THE CONSTRUCTION OF PARTICULAR DETAILS OR COMPONENTS; COMBINATIONS OR ASSOCIATIONS OF METAL-WORKING MACHINES, NOT DIRECTED TO A PARTICULAR RESULT
    • B23Q1/00—Members which are comprised in the general build-up of a form of machine, particularly relatively large fixed members
    • B23Q1/25—Movable or adjustable work or tool supports
    • B23Q1/44—Movable or adjustable work or tool supports using particular mechanisms
    • B23Q1/56—Movable or adjustable work or tool supports using particular mechanisms with sliding pairs only, the sliding pairs being the first two elements of the mechanism
    • B23Q1/60—Movable or adjustable work or tool supports using particular mechanisms with sliding pairs only, the sliding pairs being the first two elements of the mechanism two sliding pairs only, the sliding pairs being the first two elements of the mechanism
    • B23Q1/62—Movable or adjustable work or tool supports using particular mechanisms with sliding pairs only, the sliding pairs being the first two elements of the mechanism two sliding pairs only, the sliding pairs being the first two elements of the mechanism with perpendicular axes, e.g. cross-slides
    • B23Q1/621—Movable or adjustable work or tool supports using particular mechanisms with sliding pairs only, the sliding pairs being the first two elements of the mechanism two sliding pairs only, the sliding pairs being the first two elements of the mechanism with perpendicular axes, e.g. cross-slides a single sliding pair followed perpendicularly by a single sliding pair
    • B23Q1/623—Movable or adjustable work or tool supports using particular mechanisms with sliding pairs only, the sliding pairs being the first two elements of the mechanism two sliding pairs only, the sliding pairs being the first two elements of the mechanism with perpendicular axes, e.g. cross-slides a single sliding pair followed perpendicularly by a single sliding pair followed perpendicularly by a single rotating pair
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23Q—DETAILS, COMPONENTS, OR ACCESSORIES FOR MACHINE TOOLS, e.g. ARRANGEMENTS FOR COPYING OR CONTROLLING; MACHINE TOOLS IN GENERAL CHARACTERISED BY THE CONSTRUCTION OF PARTICULAR DETAILS OR COMPONENTS; COMBINATIONS OR ASSOCIATIONS OF METAL-WORKING MACHINES, NOT DIRECTED TO A PARTICULAR RESULT
    • B23Q39/00—Metal-working machines incorporating a plurality of sub-assemblies, each capable of performing a metal-working operation
    • B23Q39/02—Metal-working machines incorporating a plurality of sub-assemblies, each capable of performing a metal-working operation the sub-assemblies being capable of being brought to act at a single operating station
    • B23Q39/021—Metal-working machines incorporating a plurality of sub-assemblies, each capable of performing a metal-working operation the sub-assemblies being capable of being brought to act at a single operating station with a plurality of toolheads per workholder, whereby the toolhead is a main spindle, a multispindle, a revolver or the like
    • B23Q39/022—Metal-working machines incorporating a plurality of sub-assemblies, each capable of performing a metal-working operation the sub-assemblies being capable of being brought to act at a single operating station with a plurality of toolheads per workholder, whereby the toolhead is a main spindle, a multispindle, a revolver or the like with same working direction of toolheads on same workholder
    • B23Q39/024—Metal-working machines incorporating a plurality of sub-assemblies, each capable of performing a metal-working operation the sub-assemblies being capable of being brought to act at a single operating station with a plurality of toolheads per workholder, whereby the toolhead is a main spindle, a multispindle, a revolver or the like with same working direction of toolheads on same workholder consecutive working of toolheads
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B25—HAND TOOLS; PORTABLE POWER-DRIVEN TOOLS; MANIPULATORS
    • B25J—MANIPULATORS; CHAMBERS PROVIDED WITH MANIPULATION DEVICES
    • B25J5/00—Manipulators mounted on wheels or on carriages
    • B25J5/02—Manipulators mounted on wheels or on carriages travelling along a guideway
    • B25J5/04—Manipulators mounted on wheels or on carriages travelling along a guideway wherein the guideway is also moved, e.g. travelling crane bridge type
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B66—HOISTING; LIFTING; HAULING
    • B66F—HOISTING, LIFTING, HAULING OR PUSHING, NOT OTHERWISE PROVIDED FOR, e.g. DEVICES WHICH APPLY A LIFTING OR PUSHING FORCE DIRECTLY TO THE SURFACE OF A LOAD
    • B66F11/00—Lifting devices specially adapted for particular uses not otherwise provided for
    • B66F11/04—Lifting devices specially adapted for particular uses not otherwise provided for for movable platforms or cabins, e.g. on vehicles, permitting workmen to place themselves in any desired position for carrying out required operations

Definitions

  • the invention relates to a machining system for aircraft structural components according to the preamble of claim 1 and to a method for machining an aircraft structural component with a proposed machining system according to the preamble of claim 12.
  • the known processing system (US 5,778,505), from which the invention proceeds, has a processing station with a Aufspannrahmen for receiving the respective aircraft structural component to be processed.
  • the processing station is furthermore equipped with a processing unit in the form of a riveting unit, which has an upper tool unit with an upper tool and an associated lower tool unit with a lower tool, wherein a coaxial alignment of the tool axis of the upper tool to the tool axis of the lower tool, a riveting operation on the aircraft structural component can be performed.
  • a rivet element in the riveting tool forming the upper tool has to be jammed and has to be removed, often by hand, before the machining can be continued.
  • the respective upper tool is several meters, for example 6 m, above the ground and therefore can not be easily reached by service personnel.
  • a service platform (service platform) for the service personnel must be moved to an area below the upper tool, through which the person can easily reach the upper tool.
  • the invention is based on the problem to design the known processing system such and further that service work on the upper tool simplifies and service-related downtime can be reduced.
  • Essential is the fundamental consideration that by providing a second upper tool unit another upper tool is available, which can perform the machining or at least a part of the processing of the aircraft structural component at its instead after failure of the other upper tool. Downtimes of the processing system can be significantly reduced.
  • the processing of the aircraft structural component is interrupted only for the period in which the further upper tool unit is placed in place of the upper tool unit having the failed upper tool relative to the shared lower tool.
  • the upper tool unit with the failed upper tool is moved out of the previous processing area, in particular into a service position, while the further upper tool unit is moved into the corresponding processing area, in particular also from a service position.
  • it is possible to repair or maintain an upper tool for example, to remove a jammed rivet element, while another upper tool or a corresponding further upper tool unit allows a continuation of the processing of the aircraft structural component.
  • the machining unit in addition to a first upper tool unit having a first tool axis, which can be aligned coaxially with respect to a second tool axis of a corresponding lower tool, the machining unit also has a second upper tool unit with a first tool axis along a third tool axis.
  • the tool axis aligned upper tool wherein the third tool axis to the second tool axis can be aligned coaxially, thereby allowing that previously carried out by the first upper tool unit and the first upper tool processing can be continued from the second upper tool unit or the second upper tool
  • the second upper tool unit can thus be positioned so that the associated upper tool can be positioned in a machining position or in machining positions that correspond to the machining position or machining positions in which the upper tool of the first upper tool unit was positioned or could be positioned.
  • the respective upper tool then cooperates with the common lower tool, which assumes an assigned machining position in the case.
  • a machining position of the upper tool or lower tool is meant a position of the respective tool in which the machining of the aircraft structural component is possible.
  • the machining is a riveting or drilling operation.
  • the first upper tool unit and the second upper tool unit are movable in the same direction.
  • the direction is, in particular, a transverse direction orthogonal to the longitudinal direction and height direction.
  • the first tool axis and the third tool axis with respect to this direction or transverse direction are preferably arranged without offset relative to one another over at least a part of the travel path (claim 3). In particular, over the largest part or the entire travel distance there is no offset in said direction or transverse direction.
  • the first upper tool unit and the second upper tool unit are movable in the same plane, in particular in a plane orthogonal to the height direction (claim 4).
  • the first upper tool unit and the second upper tool unit on a common guide, in particular linear guide, movable.
  • the two upper tool units each have their own upper tool carrier, via which the connection to the guide is made (claim 6).
  • the upper tool of the first upper tool unit and the upper tool of the second upper tool unit are connected via a common upper tool carrier with said guide.
  • the guide is according to the embodiment according to claim 7 part of an upper frame part of a frame of the processing plant.
  • the upper frame part runs in this case in particular along the transverse direction.
  • the frame can also have a lower frame part, which also extends in particular along the transverse direction, and one or two lateral frame parts which connect the upper frame part to the lower frame part.
  • the frame may have a portal-like or C-shaped configuration.
  • the guide is in such a frame, in particular at the bottom of the upper frame part, in particular at a height of at least 5 m, preferably at least 6 m, more preferably at least 7 m arranged.
  • Such a frame allows a suitable working height for the processing of various aircraft structural components, such as hulls or wings.
  • the working height ie the point at which the upper tool cooperates with the lower tool as intended lies in particular in a range of 5 m to 7 m, preferably in a range of 5.5 m to 6.5 m, particularly preferably in one range from 5.5 m to 6 m.
  • the upper tool units are independently movable and / or independently operable in the processing unit.
  • one of the upper tool units can be taken out of operation, while the other upper tool unit performs the appropriate work with their upper tool.
  • the other upper tool unit can be arranged in a service position in which this upper tool unit in particular does not influence the functioning of the other upper tool unit.
  • the upper tool unit which is not in the service position, can thereby be positioned so that the associated tool axis can be aligned coaxially with the second tool axis, that is, with the tool axis of the lower tool.
  • Claim 9 defines various embodiments of the respective upper tool or equipping the respective upper tool unit with certain upper tools.
  • a riveting tool or a drilling tool can be provided as an upper tool.
  • the respective upper tool unit may be a combined upper tool unit with a riveting tool and a drilling tool.
  • Claim 10 defines drive options that allow the said movements, in particular linear movements, the first and / or second upper tool unit.
  • FIG. 1a shows a proposed processing system during processing of an aircraft structural component in a perspective view
  • FIG. 1b the processing system of FIG. 1a in a sectional view.
  • the illustrated processing plant 1 is used for processing aircraft structural components 2, which, as mentioned above, may be hulls, wings or other large aircraft structural components 2.
  • the processing plant 1 has a processing station 3.
  • the processing station 3 has on the one hand a Tomspannrahmen 4 for receiving the respective aircraft structural component 2 to be processed and on the other hand, a processing unit 5 for the processing of the aircraft structural component 2.
  • the Aufspannrahmen 4 extends along a station longitudinal axis 6, which extends in a longitudinal direction X of the processing plant 1.
  • the extension of the Aufspannrahmens 4 along the station longitudinal axis 6 is to be understood. It means that the Aufspannrahmen 4 extends at least in a basic position parallel to the station longitudinal axis 6, for example, when the Aufspannrahmen 4 is vertically aligned and / or oriented horizontally.
  • the Aufspannrahmen 4 is here and preferably at two positioning towers 7, 8, which extend parallel to the height direction Z, height-adjustable and pivotally articulated.
  • the height adjustment is indicated in Fig. 1a by the reference numeral 9 and the pivoting with the reference numeral 10.
  • the height adjustment 9 for the two positioning towers 7, 8 may be possible separately, so that tilting of the Aufspannrahmens 4 about a transverse to the station longitudinal axis 6 extending tilting axis (not shown here) can be realized.
  • the machining unit 5 comprises a first upper tool unit 11 with an upper tool 13 aligned along a first tool axis 12a and an associated lower tool unit 14 with a lower tool 15 aligned along a second tool axis 12b.
  • the machining unit 5 comprises at least one second upper tool unit 11 ', here and preferably exactly one second upper tool unit 11', with an upper tool 13 'aligned along a third tool axis 12a', wherein the lower tool unit 14 is likewise assigned to the second upper tool unit 11 '
  • the respective upper tool unit 11, 11 'and the common lower tool unit 14 each form an end effector, wherein the respective upper tool 13, 13' is in particular a rivet head or drill head and the lower tool 15 forms the corresponding counterpart thereto.
  • One of the two upper tool units 11, 11 'or both upper tool units 11, 11' can also have more than one upper tool 13, 13 ', in particular a rivet head and / or drill head.
  • both upper tool units 11, 11 'each have both a rivet head and a drill head.
  • the upper tool units 11, 11' can replace each other during machining of the aircraft structural component 2, if necessary.
  • the first upper tool unit 11 in a riveting operation, which is performed by the first upper tool unit 11 with the first upper tool 13, a rivet element jammed in the upper tool 13, whereby this upper tool unit 11 is temporarily no longer functional.
  • the second upper tool unit 11 ' instead of the first upper tool unit 11, the second upper tool unit 11 'can be operated with one or more upper tools 13' corresponding to the upper tool 13 of the first upper tool unit 11, in conjunction with the same lower tool unit 14 as before.
  • the second upper tool unit 11 'then takes over the function of the first upper tool unit 11, which is taken out of service during this time.
  • it can be repaired or maintained.
  • a jammed rivet element can be removed from the upper tool 13.
  • the upper tool 13 'of the second upper tool unit 11' is preferably effected in the same way as the machining by means of the first upper tool unit 11 and the upper tool 13 of the first upper tool unit 11.
  • the first tool axis 12a of the upper tool 13 of the first upper tool unit 11 and the second tool axis 12b of Lower tool 15 extend here in one direction at an angle and in particular orthogonal to the longitudinal direction X. This direction is also referred to herein as height direction Z.
  • the first tool axis 12a and the second tool axis 12b are in the embodiment in Figs.
  • first upper tool unit 11 in each processing position of the upper tool 13 of the activated here first upper tool unit 11 and the lower tool 15 coaxially aligned, so both extend in alignment in the height direction Z.
  • this can be moved to a service position (shown in dashed lines in FIGS. 1 a and b) and the second upper tool unit 11 'can be moved to the next Machining of the aircraft structural component 2 to be moved from the left (inactive) position shown in FIGS. 1a and b in the position in which previously the first upper tool unit 11 was located.
  • the third tool axis 12a' and the second tool axis 12b also extend in the direction of angled and in particular orthogonal to the longitudinal direction X, that is the height direction Z, in which case the third tool axis 12a ' and the second tool axis 12b are aligned coaxially with each other, so also both aligned in the height direction Z.
  • the adjustability or Verfahrbarkelt of the lower tool 15 and the lower tool unit 14 is in Fig. 1b with the reference numeral 19 and the adjustability or Verfahr- Availability of the upper tools 13, 13 'and the upper tool units 11, 11' indicated by the reference numeral 20.
  • the respective upper tool 13, 13 'and the lower tool 15 are each mounted on an associated tool carrier 16, 16', 17 in the embodiment described here, namely the upper tool 13 on an upper tool carrier 16, the upper tool 13 'on an upper tool carrier 16' and the Lower tool 15 on a lower tool carrier 17, wherein the tool carrier 16, 16 ', 17 each part of the respective Oberwerkmaschinemaschineei- beauty 11, 11' and lower tool unit 14 is.
  • the lower tool carrier 17 is rotatable here about a lower tool carrier axis 18 which is parallel to the height direction Z and forms an axis of rotation, in particular by at least 180 °, preferably by at least 360 °, which is indicated here by the reference numeral 24.
  • the lower tool carrier 17 here and preferably in an orthogonal to the longitudinal direction X and height direction Z transverse direction Y is adjustable or movable, which is indicated here by the reference numeral 25.
  • the lower tool carrier 17 comprises an upper support member 17a in the form of a support beam 17a and a lateral support member 17b in the form of a Supporting column 17b, wherein the supporting beam is also adjustable or movable relative to the support column 17b in the height direction Z, which is indicated in Fig. 1b by the reference numeral 26.
  • the first upper tool unit 11 and the second upper tool unit 11' here and preferably in the same direction, namely in the transverse direction Y. , linearly movable over a travel distance 27, 27 '.
  • the travel distances 27, 27 ' are shown in FIG. 1b. It should be pointed out that the first upper tool unit 11 and / or second upper tool unit 11 'for machining an aircraft structural component 2 can in principle also be moved beyond the travel distances 27, 27' shown here, if necessary. As can be seen from FIG.
  • the tool axis 12 a of the upper tool 13 of the first upper tool unit 11 (first tool axis) and the tool axis 12 a 'of the upper tool 13 * of the second upper tool unit 11' (third tool axis) are here and preferably in relation to the transverse direction Y
  • upper tool units 11, 11 ' also run in the same plane, which extends here orthogonally to the height direction Z.
  • the processing plant 1 here has a portal-shaped frame 22, which has a lower frame part 22a, which here also extends in the transverse direction Y.
  • the lower frame part 22a is connected on both sides to two frame parts 22b, 22c extending in the height direction Z, which are spaced apart in the transverse direction Y and carry an upper frame part 22d, which also extends in the transverse direction Y.
  • the upper frame part 22d in turn has a guide 28, in particular a linear guide, which is part of the upper frame part 22d.
  • the upper tool 13 of the first upper tool unit 11 and the upper tool 13 'of the second upper tool unit 11' are each movably guided on the guide 28 by means of their respective associated upper tool carrier 16, 16 'on which they are mounted.
  • the guide 28 is formed here and preferably as a common guide 28 for both upper tool units 11, 11 '.
  • the Aufspannrahmen 4 In the area within the frame 22, the Materialsspannrahmen 4, to which the aircraft structural component 2 to be machined is attached runs.
  • the Aufspannrahmen 4 is, as previously explained, within the frame 22 about the longitudinal axis of the frame 21, which is here parallel to the station longitudinal axis 6, but also can be tilted to this, pivotable.
  • the frame 22 of the processing installation 1 can in principle also be designed differently in order to support the upper tool units 11, 11 '.
  • the frame 22 is C-shaped, so only a single lateral Frame part 22b, which connects the lower frame part 22a with the upper frame part 22d.
  • the lower tool carrier 18, in contrast to the exemplary embodiment illustrated here would have to be arranged independently of the frame 22 on the lower surface 23.
  • the lower tool support 18, as in the present case, with the frame 22, or on the lower frame part 22 a, to arrange, since in this way the whole of frame 22, the two upper tool units 11, 11 'and Lower tool unit 14 relative to the Aufspannrahmen 4 and the aircraft structural component 2 in the longitudinal direction X or along the station longitudinal axis 6 can be moved, the upper tool units 11, 11 ', when they are active, remain optimally aligned with the lower tool unit 14.
  • the mobility of the frame 22 is indicated in Fig. 1a by the reference numeral 29.
  • the two upper tool units 11, 11 ' which here preferably each have both a riveting tool and a drilling tool, can be moved independently of one another and, as already indicated, can also be operated independently of one another (can be activated).
  • the processing system 1 here and preferably has two drive motors (not shown), of which a first drive motor of the first upper tool unit 11 and a second drive motor of the second upper tool unit 11 'is assigned.
  • the drive motors can be actuated independently of each other. In principle, however, it is also conceivable to move the first upper tool unit 11 and the second upper tool unit 11 'via a common drive motor.
  • the proposed processing plant 1 further comprise one or more of the following drive motors:
  • a drive motor for a linear movement of the support bar 17a of the lower tool carrier 17, in particular relative to the support column 17b of the lower tool carrier 17,
  • a drive motor for the linear movement of the lower frame part 22a or of the frame 22, in particular relative to the base 23.
  • one of the upper tool units 11, 11 ' is operated by the formation of the proposed processing system 1 during processing, in particular during a riveting or drilling operation, while the other of the upper tool units 11, 11' except Operation is and / or arranged in a service position.
  • the processing of the aircraft structural component 2 instead of the to be repaired or maintained tool unit takes over. Downtime of the processing plant 1 can be reduced in this way to a minimum.

Abstract

L'invention concerne une installation de traitement de composants structuraux d'aéronef (2) comportant une station de traitement (3) comprenant un cadre de serrage (4) destiné à recevoir le composant structural d'aéronef (2) à traiter, le cadre de serrage (4) s'étendant le long d'un axe longitudinal (6) de la station dans une direction longitudinale (X), et une unité d'usinage (5) pour usiner l'élément structurel d'aéronef (2) comprenant une première unité d'outil supérieure (11) ayant un outil supérieur (13) orienté le long d'un premier axe d'outil (12a) et une unité d'outil inférieure (14) ayant un outil inférieur (15) orienté le long d'un second axe d'outil (12b), dans laquelle le premier axe d'outil (12a) et le deuxième axe d'outil (12b) sont orientés et/ou peuvent être orientés parallèlement à une direction de hauteur (Z) angulaire, en particulier orthogonale, à la direction longitudinale (X), et dans laquelle dans au moins une position d'usinage de l'outil supérieur (13) du premier outil supérieur (11) et dans au moins une position d'usinage de l'outil inférieur (15) du dispositif inférieur (14) le premier axe d'outil (12a) et le deuxième axe d'outil (12b) sont orientés coaxialement entre eux. Selon l'invention, l'unité d'usinage (5) comporte une deuxième unité d'usinage supérieure (11') ayant un outil supérieur (13') orienté le long d'un troisième axe d'outil (12a'), le troisième axe d'outil (12a') étant orienté ou orientable parallèlement à la direction en hauteur (Z), et en ce que dans au moins une position d'usinage de l'outil supérieur (13') de la deuxième unité d'outil supérieure (11') et dans au moins une position d'usinage de l'outil inférieur (15) de l'unité d'outil inférieure (14), le deuxième axe d'outil (12b) et le troisième axe d'outil (12a') sont orientés coaxialement.
EP18722010.8A 2017-07-24 2018-04-27 Installation d'usinage pour éléments structuraux d'avions Active EP3658462B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102017116718.8A DE102017116718A1 (de) 2017-07-24 2017-07-24 Bearbeitungsanlage für Flugzeugstrukturbauteile
PCT/EP2018/060898 WO2019020226A1 (fr) 2017-07-24 2018-04-27 Installation d'usinage pour éléments structuraux d'avions

Publications (2)

Publication Number Publication Date
EP3658462A1 true EP3658462A1 (fr) 2020-06-03
EP3658462B1 EP3658462B1 (fr) 2022-09-14

Family

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP18722010.8A Active EP3658462B1 (fr) 2017-07-24 2018-04-27 Installation d'usinage pour éléments structuraux d'avions

Country Status (7)

Country Link
US (1) US20200207487A1 (fr)
EP (1) EP3658462B1 (fr)
CN (1) CN111132903B (fr)
DE (1) DE102017116718A1 (fr)
ES (1) ES2930014T3 (fr)
RU (1) RU2751475C1 (fr)
WO (1) WO2019020226A1 (fr)

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Publication number Priority date Publication date Assignee Title
CN110356583B (zh) * 2019-06-28 2021-07-02 西安航空学院 一种飞机机翼装配用调节装置
CN110356584B (zh) * 2019-06-28 2021-06-22 西安航空学院 一种飞机机翼装配用调节方法

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WO2019020226A1 (fr) 2019-01-31
RU2751475C1 (ru) 2021-07-14
CN111132903B (zh) 2023-09-19
EP3658462B1 (fr) 2022-09-14
CN111132903A (zh) 2020-05-08
DE102017116718A1 (de) 2019-01-24
US20200207487A1 (en) 2020-07-02

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